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N-14 (n14-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: N-14 (n14-il)
Reynolds number: 200,000
Max Cl/Cd: 48.35 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n14-il-200000.txt
Download as CSV file: xf-n14-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-14                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5285   0.10020   0.09644  -0.0315   1.0000   0.0725
 -12.000  -0.9447   0.05213   0.04701  -0.0499   1.0000   0.0438
 -11.750  -0.9701   0.04918   0.04378  -0.0450   1.0000   0.0435
 -11.500  -0.9862   0.04678   0.04118  -0.0400   1.0000   0.0436
 -11.250  -0.9915   0.04449   0.03873  -0.0364   1.0000   0.0441
 -11.000  -0.9943   0.04217   0.03620  -0.0328   1.0000   0.0445
 -10.750  -0.9859   0.04085   0.03485  -0.0305   1.0000   0.0458
 -10.500  -0.9846   0.03896   0.03276  -0.0271   1.0000   0.0467
 -10.250  -0.9826   0.03698   0.03052  -0.0235   1.0000   0.0477
 -10.000  -0.9788   0.03497   0.02821  -0.0201   1.0000   0.0485
  -9.750  -0.9721   0.03310   0.02605  -0.0169   1.0000   0.0493
  -9.500  -0.9632   0.03167   0.02432  -0.0138   1.0000   0.0502
  -9.250  -0.9527   0.02991   0.02227  -0.0111   1.0000   0.0512
  -9.000  -0.9358   0.02768   0.01999  -0.0098   1.0000   0.0530
  -8.750  -0.9195   0.02648   0.01873  -0.0080   1.0000   0.0544
  -8.500  -0.9030   0.02536   0.01751  -0.0061   1.0000   0.0558
  -8.250  -0.8867   0.02439   0.01644  -0.0041   1.0000   0.0576
  -8.000  -0.8700   0.02349   0.01540  -0.0020   1.0000   0.0593
  -7.750  -0.8531   0.02262   0.01440   0.0000   1.0000   0.0606
  -7.500  -0.8368   0.02125   0.01306   0.0019   1.0000   0.0626
  -7.250  -0.8221   0.02055   0.01237   0.0042   1.0000   0.0648
  -7.000  -0.8074   0.01996   0.01175   0.0065   1.0000   0.0672
  -6.750  -0.7927   0.01939   0.01112   0.0090   1.0000   0.0698
  -6.500  -0.7797   0.01870   0.01043   0.0117   1.0000   0.0723
  -6.250  -0.7662   0.01823   0.01000   0.0142   1.0000   0.0757
  -6.000  -0.7515   0.01787   0.00961   0.0166   1.0000   0.0803
  -5.750  -0.7376   0.01746   0.00922   0.0191   1.0000   0.0863
  -5.500  -0.7222   0.01714   0.00888   0.0214   1.0000   0.0955
  -5.250  -0.7095   0.01656   0.00836   0.0240   1.0000   0.1109
  -5.000  -0.6975   0.01591   0.00782   0.0267   1.0000   0.1309
  -4.750  -0.6832   0.01548   0.00744   0.0289   1.0000   0.1484
  -4.500  -0.6676   0.01516   0.00718   0.0309   1.0000   0.1641
  -4.250  -0.6515   0.01489   0.00696   0.0328   1.0000   0.1803
  -4.000  -0.6300   0.01460   0.00679   0.0336   0.9989   0.2016
  -3.750  -0.5965   0.01431   0.00671   0.0319   0.9947   0.2442
  -3.500  -0.5663   0.01390   0.00660   0.0308   0.9900   0.3063
  -3.250  -0.5365   0.01343   0.00652   0.0299   0.9851   0.3820
  -3.000  -0.5110   0.01291   0.00646   0.0299   0.9799   0.4759
  -2.750  -0.4879   0.01239   0.00653   0.0308   0.9740   0.5935
  -2.500  -0.4565   0.01221   0.00683   0.0304   0.9702   0.7013
  -2.250  -0.4312   0.01213   0.00693   0.0313   0.9636   0.7577
  -2.000  -0.3953   0.01222   0.00708   0.0300   0.9591   0.7988
  -1.750  -0.3554   0.01232   0.00722   0.0280   0.9540   0.8313
  -1.500  -0.3142   0.01240   0.00732   0.0258   0.9474   0.8562
  -1.250  -0.2633   0.01250   0.00739   0.0217   0.9433   0.8756
  -1.000  -0.2194   0.01262   0.00750   0.0190   0.9370   0.8915
  -0.750  -0.1664   0.01272   0.00757   0.0144   0.9319   0.9014
  -0.500  -0.1129   0.01270   0.00751   0.0097   0.9281   0.9110
  -0.250  -0.0489   0.01284   0.00763   0.0029   0.9268   0.9152
   0.000  -0.0056   0.01299   0.00778   0.0002   0.9203   0.9234
   0.250   0.0503   0.01301   0.00781  -0.0051   0.9169   0.9278
   0.500   0.1139   0.01302   0.00783  -0.0119   0.9144   0.9302
   0.750   0.1853   0.01305   0.00791  -0.0197   0.9114   0.9374
   1.000   0.2488   0.01304   0.00794  -0.0259   0.9002   0.9462
   1.250   0.3030   0.01283   0.00775  -0.0306   0.8847   0.9525
   1.500   0.3454   0.01259   0.00749  -0.0330   0.8643   0.9571
   1.750   0.3878   0.01238   0.00728  -0.0356   0.8398   0.9603
   2.000   0.4251   0.01224   0.00709  -0.0371   0.8102   0.9649
   2.250   0.4543   0.01218   0.00696  -0.0370   0.7743   0.9709
   2.500   0.4904   0.01203   0.00670  -0.0384   0.7246   0.9750
   2.750   0.5194   0.01207   0.00649  -0.0383   0.6554   0.9807
   3.000   0.5476   0.01229   0.00628  -0.0383   0.5635   0.9857
   3.250   0.5747   0.01268   0.00620  -0.0384   0.4688   0.9911
   3.500   0.6043   0.01303   0.00620  -0.0392   0.4038   0.9959
   3.750   0.6356   0.01329   0.00623  -0.0404   0.3571   1.0000
   4.000   0.6513   0.01356   0.00640  -0.0383   0.3263   1.0000
   4.250   0.6672   0.01383   0.00657  -0.0363   0.2949   1.0000
   4.500   0.6827   0.01412   0.00673  -0.0343   0.2570   1.0000
   4.750   0.6970   0.01451   0.00691  -0.0320   0.2067   1.0000
   5.000   0.7092   0.01513   0.00725  -0.0294   0.1604   1.0000
   5.250   0.7202   0.01589   0.00777  -0.0265   0.1264   1.0000
   5.500   0.7324   0.01655   0.00829  -0.0238   0.1091   1.0000
   5.750   0.7467   0.01699   0.00872  -0.0214   0.0989   1.0000
   6.000   0.7603   0.01751   0.00925  -0.0188   0.0924   1.0000
   6.250   0.7746   0.01796   0.00970  -0.0163   0.0870   1.0000
   6.500   0.7871   0.01863   0.01032  -0.0136   0.0827   1.0000
   6.750   0.8020   0.01910   0.01086  -0.0112   0.0789   1.0000
   7.000   0.8162   0.01965   0.01142  -0.0087   0.0756   1.0000
   7.250   0.8295   0.02058   0.01228  -0.0063   0.0722   1.0000
   7.500   0.8450   0.02128   0.01307  -0.0040   0.0696   1.0000
   7.750   0.8607   0.02200   0.01386  -0.0018   0.0669   1.0000
   8.000   0.8763   0.02276   0.01463   0.0004   0.0641   1.0000
   8.250   0.8947   0.02453   0.01635   0.0016   0.0608   1.0000
   8.500   0.9100   0.02526   0.01726   0.0040   0.0591   1.0000
   8.750   0.9255   0.02622   0.01837   0.0061   0.0568   1.0000
   9.000   0.9407   0.02719   0.01942   0.0082   0.0545   1.0000
   9.250   0.9573   0.02854   0.02075   0.0098   0.0521   1.0000
   9.500   0.9718   0.03110   0.02351   0.0116   0.0503   1.0000
   9.750   0.9809   0.03214   0.02483   0.0148   0.0489   1.0000
  10.000   0.9897   0.03351   0.02645   0.0178   0.0473   1.0000
  10.250   0.9992   0.03485   0.02795   0.0205   0.0456   1.0000
  10.500   1.0103   0.03614   0.02928   0.0227   0.0440   1.0000
  10.750   1.0202   0.03828   0.03149   0.0247   0.0429   1.0000
  11.000   1.0196   0.04238   0.03584   0.0276   0.0420   1.0000
  11.250   1.0114   0.04373   0.03755   0.0326   0.0415   1.0000
  11.500   1.0009   0.04565   0.03976   0.0374   0.0410   1.0000
  11.750   0.9844   0.04755   0.04191   0.0428   0.0406   1.0000
  12.000   0.9658   0.04984   0.04443   0.0475   0.0403   1.0000
  12.250   0.9449   0.05256   0.04739   0.0512   0.0399   1.0000
  12.500   0.9222   0.05590   0.05096   0.0535   0.0397   1.0000
  12.750   0.8975   0.06011   0.05537   0.0543   0.0399   1.0000
  13.000   0.8691   0.06532   0.06079   0.0535   0.0402   1.0000
  13.250   0.8403   0.07152   0.06715   0.0508   0.0405   1.0000
  13.500   0.8103   0.07919   0.07495   0.0464   0.0411   1.0000
  13.750   0.7854   0.08738   0.08321   0.0420   0.0417   1.0000
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